Updating of finite element model of aircraft structure according results of ground vibration test

Abstract

This paper deals with updating of the aircraft structure finite element (FE) model according ground vibration test (GVT) results. Paper describes possible approaches of flutter analysis as regards to the incorporation of GVT results including: (1) the direct usage of GVT results and (2) updating of analytical FE model. Then the theoretical background of the model updating methods including Bayesian parameter estimation and more generic optimization using powerful nonlinear gradient-based methods are given. Finally, the methodology of an aircraft structure FE model updating is described. The practical application of the procedure is documented on the EV-55M turboprop utility aircraft example. Selected results are shown, evaluated and the conclusions are formulated.

Keywords

Aeroelasticity model updating ground vibration test Bayesian estimation EV-55M aircraft

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